CN101769165B - Positive displacement gas turbine engine with parallel screw rotors - Google Patents

Positive displacement gas turbine engine with parallel screw rotors Download PDF

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Publication number
CN101769165B
CN101769165B CN200910113700.0A CN200910113700A CN101769165B CN 101769165 B CN101769165 B CN 101769165B CN 200910113700 A CN200910113700 A CN 200910113700A CN 101769165 B CN101769165 B CN 101769165B
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CN
China
Prior art keywords
main
rotor
lock
helical blade
wheel hub
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Expired - Fee Related
Application number
CN200910113700.0A
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Chinese (zh)
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CN101769165A (en
Inventor
K·D·穆罗
R·G·吉芬
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General Electric Co
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General Electric Co
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Publication of CN101769165B publication Critical patent/CN101769165B/en
Expired - Fee Related legal-status Critical Current
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01C—ROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
    • F01C1/00—Rotary-piston machines or engines
    • F01C1/08—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing
    • F01C1/12—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing of other than internal-axis type
    • F01C1/14—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons
    • F01C1/16—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons with helical teeth, e.g. chevron-shaped, screw type
    • F01C1/165—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons with helical teeth, e.g. chevron-shaped, screw type having more than two rotary pistons with parallel axes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01C—ROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
    • F01C1/00—Rotary-piston machines or engines
    • F01C1/08—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing
    • F01C1/12—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing of other than internal-axis type
    • F01C1/14—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons
    • F01C1/20—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons with dissimilar tooth forms
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01C—ROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
    • F01C11/00—Combinations of two or more machines or engines, each being of rotary-piston or oscillating-piston type
    • F01C11/002—Combinations of two or more machines or engines, each being of rotary-piston or oscillating-piston type of similar working principle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
    • F04C29/00—Component parts, details or accessories of pumps or pumping installations, not provided for in groups F04C18/00 - F04C28/00
    • F04C29/12—Arrangements for admission or discharge of the working fluid, e.g. constructional features of the inlet or outlet
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01C—ROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
    • F01C11/00—Combinations of two or more machines or engines, each being of rotary-piston or oscillating-piston type
    • F01C11/006—Combinations of two or more machines or engines, each being of rotary-piston or oscillating-piston type of dissimilar working principle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
    • F04C2240/00—Components
    • F04C2240/20—Rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
    • F04C2250/00—Geometry
    • F04C2250/10—Geometry of the inlet or outlet
    • F04C2250/101—Geometry of the inlet or outlet of the inlet
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
    • F04C2250/00—Geometry
    • F04C2250/10—Geometry of the inlet or outlet
    • F04C2250/102—Geometry of the inlet or outlet of the outlet

Abstract

The invention relates to a positive displacement gas turbine engine with parallel screw rotors. An axial flow positive displacement gas turbine engine component such as a compressor or a turbine or an expander includes a rotor assembly extending from a fully axial flow inlet to a downstream axially spaced apart axial flow outlet. The rotor assembly includes a main rotor and one or more gate rotors rotatable about parallel main and gate axes of the main and gate rotors respectively. The main and gate rotors having intermeshed main and gate helical blades extending radially outwardly from annular main and gate hubs, circumscribed about, and wound about the main and gate axes respectively. Intersecting main and gate annular openings in the axial flow inlet extend radially between a casing surrounding the rotor assembly and the main and gate hubs. The main helical blades transition from 0 to a full radial height in a downstream direction in an inlet transition section.

Description

With having of axial flow entrance and exit positive displacement rotating member main, gate rotor
Technical field
The present invention relates generally to positive displacement (positive displacement) rotating machinery and motor and their member, and relates more specifically to have this class machinery and member of main rotor and gate rotor (gaterotor).
Background technique
Axial flow positive displacement rotating machinery is for pump, turbine, compressor and motor, and is commonly referred to as screw pump, screw type turbine and screw compressor.Published, the positive displacement rotating machinery with main rotor and gate rotor can be used for turbine and compressor.The common use of axial flow turbine radially fills vaned member, for example the fan in various types of gas turbine engines, compressor and turbine.Axial flow turbine is with a wide range of applications using energy acting or obtain from working fluid aspect energy, because the oriented given proparea of axial flow turbine (frontal area) provides high mass velocity and continuous approaches the integration capability that stable fluid flows.Turbine design person's target is the turbine components or machinery and the motor that provide lightweight and compact.Another target is to make turbine to have the least possible part, to reduce manufacture, installation, trimming, maintenance and to change member or the cost of machinery.
Summary of the invention
The member of axial flow positive displacement gas turbine engine comprises the rotor assembly that extends to downstream axially spaced axial flow outlet from holoaxial streaming entrance, and comprises main rotor and one or more gate rotor.Main rotor and gate rotor can be respectively around the main axis departing from substantially in parallel of main rotor and gate rotor and the rotation of lock axis.Main rotor and gate rotor have respectively intermeshing main helical blade and the lock helical blade of reeling around main axis and lock axis, and main helical blade and lock helical blade radially outwards extend from being defined as around annular main wheel hub and the circular brake wheel hub of main axis and lock axis.
An exemplary embodiment of member comprises respectively crossing main loop opening and the lock annular opening radially extending between the housing of rotor assembly and main wheel hub and brake wheel hub holding.Gearing (gearing) makes main rotor synchronous together with gate rotor.
The middle body of main helical blade extends vertically and downstream, and has the full radial height radially outwards recording from main wheel hub.Entrance changeover portion is positioned at axial the place ahead and the upstream of middle body.In entrance changeover portion, main helical blade is transitioned into from 0 radial height the blade profile launching completely on downstream direction, and this blade profile launching completely has from the radially measured full radial height of main wheel hub.
Member can have the outlet changeover portion in the axial rearward direction of middle body and downstream, and wherein, main helical blade is transitioned into from 0 radially measured radial height of main wheel hub from having the blade profile launching completely of full radial height on downstream direction.
Main helical blade and lock helical blade can rotate in stream, and this stream is disposed radially between main wheel hub and brake wheel hub and housing, and extend to downstream vertically axial flow outlet from axial flow entrance.Stream comprises with crossfire relation downstream inlet streams section, the annular central flowpath segment being arranged in entrance changeover portion, and is arranged on the outlet flowpath segment in outlet changeover portion.The annular entry area in inlet streams section is less than the annular exit area in inlet streams section.Outlet flowpath segment also can have the circular crosssection area reducing on downstream direction.
The main helical blade of rotor assembly has the first different main torsion slopes (slope) and the second main torsion slope respectively in the first paragraph of rotor assembly and second segment, and lock helical blade has respectively in this first paragraph and second segment, the first different locks reverses slope and the second lock reverses slope.
A compressor that embodiment is axial flow positive displacement gas turbine engine of axial flow positive displacement gas turbine engine component, wherein, the first main torsion slope and the first lock reverse slope and are less than respectively the second main torsion slope and the second lock torsion slope.Another embodiment of axial flow positive displacement gas turbine engine component is the turbine of axial flow positive displacement gas turbine engine, and wherein, the first main torsion slope and the first lock reverse slope and be greater than respectively the second main torsion slope and the second lock torsion slope.
Accompanying drawing explanation
Fig. 1 is the perspective view with the axial flow entrance positive-displacement compressor of main rotor and a gate rotor.
Fig. 2 is the main rotor of the rotor assembly of compressor shown in Fig. 1 and the perspective view of seeing from front to back of gate rotor.
Fig. 3 is the main rotor of the rotor assembly shown in Fig. 1 and the perspective view of seeing from back to front of gate rotor.
Fig. 4 is the perspective view of seeing from the top down through the first compressing section of rotor assembly shown in Fig. 2 and the main rotor of the second compressing section and gate rotor.
Fig. 5 is the perspective view from the side of the main rotor in the compressing section of rotor assembly shown in Fig. 2.
Fig. 6 is the perspective view from the side of the gate rotor in the compressing section of rotor assembly shown in Fig. 2.
Fig. 7 is the sectional view of the vane collocation (blading) of the main rotor with three helical blades or blade profile part of compressor shown in Fig. 2 and Fig. 3 and the gate rotor with four helical blades or blade profile part (lobe).
Fig. 8 is the perspective view of compressing section with the rotor shaft streaming entrance positive-displacement compressor of main rotor and two gate rotors.
Fig. 9 is the main rotor of rotor assembly shown in Fig. 8 and the perspective view of two gate rotors.
Figure 10 be shown in Fig. 8 and Fig. 9 in the changeover portion of suction port of compressor main rotor helical blade scan the perspective view that leading edge is seen downstream.
Figure 11 be main rotor helical blade shown in Figure 10 scan leading edge perspective view from the side.
Figure 12 is the perspective view of the helical blade trailing edge of main rotor in the outlet changeover portion of compressor shown in Fig. 8 and Fig. 9.
Figure 13 is having with the main rotor of four helical blades or blade profile part and the cross-sectional of arranging with the alternative blade of the rotor assembly of the gate rotor of three helical blades or blade profile part shown in Fig. 8.
Figure 14 is having with the main rotor of six helical blades or blade profile part and the cross-sectional of arranging with the alternative blade of the rotor assembly of the gate rotor of four helical blades or blade profile part shown in Fig. 8.
Figure 15 is having with the main rotor of eight helical blades or blade profile part and the sectional view arranged with the alternative blade of the gate rotor of five helical blades or blade profile part shown in Fig. 8.
Figure 16 is the cross-sectional of gearing of the rotor assembly of the compressor shown in Fig. 1.
Figure 17 is the cross-sectional of gearing of the rotor assembly of the compressor shown in Fig. 8.
Figure 18 is the cross-sectional with the axial flow entrance positive displacement expander (expander) of main rotor and a gate rotor.
Figure 19 is the cross-sectional with the axial flow entrance positive displacement expander of main rotor and two gate rotors.
Figure 20 is the perspective view of seeing from front to back that scans leading edge of the main rotor helical blade in the changeover portion of expander entrance shown in Figure 18.
Figure 21 is the perspective view of seeing from front to back of the main rotor helical blade trailing edge in the outlet of expander shown in Figure 18 and Figure 20 changeover portion.
Figure 22 is the side perspective view of the helical blade trailing edge of main rotor in expander shown in Figure 22 outlet changeover portion and gate rotor.
Figure 23 is the cross-sectional of rotor assembly with the compressor of two main rotors and a gate rotor.
Figure 24 is the cross-sectional of rotor assembly with the compressor of two main rotors and two gate rotors.
Figure 25 is the sectional view of the main rotor of compressor shown in Figure 23 and the vane collocation of gate rotor.
Figure 26 is the sectional view with the vane collocation of the rotor assembly of the compressor of two main rotors and a gate rotor, and these two main rotors and a gate rotor have the not axis in a plane.Parts list 0 point 3 of the gas turbine engine component 7 gate rotor 8 gas turbine engine compressor compressor housing 10 9 main annular opening ring opening of 11 gate 12 gate rotor main rotor 13 of the first 14 second 15 16 gate rotor rotor assembly of principal axis 17 main spiral blade 18 gate 19 gate axis 20 axis of the first 21 principal screw entrance surface 22 export 23 first gate spiral surface 24 of the first compression section 25 26 second working fluid compression section 27 first gate helical blade 28 inlet transition section 29 gate second helical blade outlet transition section 32 of the first 30 gate 33 gate second helical torsion slope 34 first principal torsional slope 35 gate second reverse slope of 36 main reverse slope of 37 power second axis 39 second gate axis 40 flow path 41 section 43 a circle at the top of the 45 44 two adjacent main rotor flow path 47 main spiral edge 48 of the first spiral edge gateThe 49 gate second spiral edge 50 filled with air 51 Main Hub 53 first gate 55 gate second wheel hub 57 main leaf type piece 58 spiral groove 59 trailing edge gate 67 leaf type piece 68 piece 69 first gate leaf type second gate leaf type piece 70 central stream sections 72 external wheel hub surface 74 ring within the casing 76 entrance flow section 78 section 79 of the compressor outlet stream flow path 80 gear device 82 gear box 84 gear 88 turbo 90 entrance hub face 92 conical entrance casing 94 conical export hub face 96 conical shell decent export 100 two rotors 102 embodiment three rotors embodiment of 117 front 124 first expansion section 126 second expansion section 131 stationary flow path the central part of the turbine casing 217 170 209 230 232 external internal trailing edge trailing edge section of trailing edge section of 235 point AI ring entrance area AO annular outlet area of AC axial clearance CL shell gap C clockwise counter clockwise CA CC area CD CP compression axial distance plane CS cylindrical surface area of D downstream direction H full radial height RM RG gate main radius radius
Embodiment
Show the exemplary embodiment of compressor 8 (shown in Fig. 1 to Figure 17), turbine or the expander 88 (shown in Fig. 8 to Figure 22) of axial flow entrance positive displacement gas turbine engine herein, they have main rotor and one or more gate rotor, and representative has the axial flow positive displacement gas turbine engine component 3 of main rotor and one or more gate rotors.The axial flow positive displacement gas turbine engine component with main rotor 12 and one or more gate rotor 7 is designed in order to acting, as energy is for example entered into the working fluid 25 of continuous-flow via compressor 8, or from the working fluid 25 of continuous-flow, obtain energy, as axial flow positive displacement expander or turbine.
Fig. 1 to Fig. 7 shows the exemplary embodiment of the compressor 8 of the axial flow entrance positive displacement gas turbine engine in compressor housing 9 with main rotor 12 and gate rotor 7.Compressor 8 has rotor assembly 15, and it comprises main rotor 12 and the gate rotor 7 that extends to axial flow outlet 22 from holoaxial streaming entrance 20.Compressor housing 9 holds main rotor 12 and gate rotor 7.Fig. 8 to Figure 15 shows the second exemplary embodiment of the compressor 8 of axial flow entrance positive displacement gas turbine engine, wherein, rotor assembly 15 has three rotors that extend to axial flow outlet 22 from axial flow entrance 20, comprises main rotor 12 and the first gate rotor 13 and the second gate rotor 14.
Shown in Fig. 2 to Fig. 6, it is being the rotor assembly 15 with main rotor 12 and single gate rotor 7 of compressor 8.Rotor assembly 15 comprises intermeshing main helical blade 17 and the lock helical blade 27 of reeling around parallel main axis 16 and the lock axis 18 of main rotor 12 and gate rotor 7 respectively.As shown in concrete in Fig. 2, main helical blade 17 and lock helical blade 27 extend radially outward from main wheel hub 51 and brake wheel hub 53, and wherein, main wheel hub 51 and brake wheel hub 53 are defined as respectively around main axis 16 and lock axis 18.The first compressing section 24 of the rotor assembly 15 of compressor 8 and the second compressing section 26 have the first different main torsion slopes 34 and the second main torsion slope 36 of main helical blade 17, and the first different lock of lock helical blade 27 reverses slope 32 and the second lock reverses slope 35.Reverse slope corresponding to the pitch of the helical blade of rotor as herein described, and describe in more detail hereinafter.The middle body 170 that extends through vertically and downstream the main helical blade 17 of the first compressing section 24 and the second compressing section 26 has with from main wheel hub 51 to the measured overall diameter of the radially outside mode of housing 9 to height H.
In main helical blade 17 and lock helical blade 27 each person in the first compressing section 24 and the second compressing section 26, there is respectively the first constant main torsion slope 34 and the second main torsion slope 36 and the first constant lock and reverse slope 32 and the second lock torsion slope 35.The first main torsion slope 34 and the second main torsion slope 36 differ from one another, and the first lock reverses slope 32 and the second lock torsion slope 35 also differs from one another.Reverse cross section 41 that slope is defined as helix element (main lobe type part 57 as shown in Figure 7) along axis as the rotating amount of the per unit distance of main axis 16.As shown in Fig. 2 and Fig. 4, reverse slope and be 360 degree or 2Pi radian divided by the axial distance CD between two adjacent top 44 of for example, identical main helical margin 47 along helix element (, as shown in Figure 2 main helical blade 17 or lock helical blade 27) or lock helical margin 48.Axial distance CD is the distance of whole circle 43 helicals.In compressor, first in first paragraph 24 reverses slope and is less than the torsion of second in second segment 26 slope.
As shown in Figures 2 and 3, compressor 8 includes mouthful changeover portion 28 and outlet changeover portion 30, and they are positioned at respectively the upstream and downstream of the first compressing section 24 and the second compressing section 26 and are designed to hold the axial flow through compressor 8.The first compressing section 24 of rotor assembly 15 and compressor 8 and the second compressing section 26 are positioned between entrance changeover portion 28 and outlet changeover portion 30 with crossfire relation downstream.In entrance changeover portion 28, main helical blade 17 is transitioned into completely the blade profile launching, on downstream direction D from 0 radial height become from main wheel hub 51 radially outwards and on axial downstream D measured overall diameter to height H.In outlet changeover portion 30, the blade profile transition of main helical blade 17 from launching completely becomes from overall diameter to height H from 0 radially measured radial height of main wheel hub 51 on downstream direction D.Entrance changeover portion 28 contributes to provide the full axial flow via axial flow entrance 20, and outlet changeover portion 30 contributes to provide the full axial flow via axial flow outlet 22.
Referring to Fig. 2, stream 40 is disposed radially between main wheel hub 51 and brake wheel hub 53 and housing 9 (shown in Fig. 1), and axially extends to downstream axial flow outlet 22 from axial flow entrance 20.Main helical blade 17 and lock helical blade 27 can be in the interior rotations of stream 40.Stream 40 also comprises the main rotor stream 45 that roughly holds main rotor 12, and main helical blade 17 can be in the interior rotation of main rotor stream 45.Stream 40 comprises the annular central flowpath segment 70 for main rotor 12.Annular central flowpath segment 70 is disposed radially between main wheel hub 51 and housing 9, and axially extends between entrance changeover portion 28 and outlet changeover portion 30.Stream 40 comprises the inlet streams section 76 that is arranged in entrance changeover portion 28, is arranged on the annular central flowpath segment 70 in the first compressing section 24 and the second compressing section 26 with crossfire relation downstream, and is arranged on the outlet flowpath segment 78 in outlet changeover portion 30.
Main helical blade 17 and lock helical blade 27 have for the blade profile that completely launch of overall diameter to height H in the first compressing section 24 and the second compressing section 26, and through the first compressing section 24 and the second compressing section 26 and compressor housing 9 sealing engagement (sealing between main helical blade 17 and lock helical blade 27 and housing 9 has been shown in Fig. 7).Main helical blade 17 and lock helical blade 27 rotate through respectively inlet streams section 76, annular central flowpath segment 70 and outlet flowpath segment 78.Inlet streams section 76, annular central flowpath segment 70 and outlet flowpath segment 78 are separately positioned between compressor housing 9 and main wheel hub 51 and brake wheel hub 53.Inlet streams section 76, annular central flowpath segment 70 and outlet flowpath segment 78 form compressor stream 40, and this compressor stream 40 axially and along downstream direction D extends to axial flow outlet 22 from axial flow entrance 20.
Entrance changeover portion 28 is significantly longer than outlet changeover portion 30 because first reverse slope 34 or pitch be significantly less than the second torsion slope 36 or pitch (as at Fig. 2 to Fig. 6 clearly).Can visualize the structure without outlet changeover portion 30.
Rotor assembly 15 provides the Continuous Flow via entrance 20 and outlet 22 at compressor 8 duration of works.Independent filling air 50 is captured and is trapped in wherein by the first compressing section 24.As shown in Fig. 2 to Fig. 4, fill the compression of air 50 along with the pressure planes CP that inflation (charge) is passed between the first compressing section 24 and the second compressing section 26 from the first compressing section 24 is passed to the second compressing section 26 and occurs.Therefore, all filling air 50 is all compressed in the two time in the first compressing section 24 and the second compressing section 26 at it.
The first compressing section 24 is designed to seal whole volumes of filling air 50, and itself and axial flow entrance 20 and axial flow outlet 22 are kept apart.Once capture, fluid filling air 50 just enters in the second compressing section 26 as discharge areas through pressure planes CP, and the axial dimension of filled volume can reduce and radial dimension may also can reduce.Then fluid filling air 50 is discharged into the static stream 131 shown in Fig. 1 and Fig. 2 from the outlet changeover portion 30 in 26 downstreams, the second compressing section.In the situation that outlet Mach number is enough low, can omit outlet changeover portion 30, allow that rotor is transitioned into static stream sharp.
Main rotor and gate rotor can rotate around its corresponding axis, and can at different circumferencial direction (C and counter-clockwise CC clockwise), above rotate by the determined rotating speed of fixed relationship as shown in Figure 16.Therefore, main rotor 12 and gate rotor 7 link together with gear, so that fixing speed ratio and phase relationship that they are always provided with the gearing 80 as shown in figs. 1 and 4 and in the gear-box 82 schematically showing in Figure 16 are relative to each other rotated.Main rotor 12 can rotate around main axis 16, and gate rotor 7 can be around 18 rotations of lock axis.Power in order to drive compression machine 8 can be supplied with via line shaft 37, and in Fig. 1, Fig. 4 and Figure 16, line shaft 37 is shown and is connected on main rotor 12.Gate rotor 7 and main rotor 12 link together with gear by the timing gear 84 of the gearing 80 in gear-box 82, to provide rotor rotation suitably regularly, and there is minimum and controlled gap between their main helical blade 17 and the lock helical blade 27 of engagement.
The intermeshing main helical blade 17 and the lock helical blade 27 that in Fig. 4 to Fig. 6, show respectively main rotor 12 and gate rotor 7 and reel around main axis 16 and lock axis 18.Main helical blade 17 and lock helical blade 27 have respectively main helicoid 21 and lock helicoid 23.Between entrance changeover portion 28 and outlet changeover portion 30, main helical blade 17 radially outwards extends from the ring surface CS of the annular main wheel hub 51 of main rotor 12.Lock helical blade 27 radially outwards extends from the brake wheel hub 53 of gate rotor 7.Ring surface CS and annular main wheel hub 51 are shown taper shape, but also can be such as columniform other shape.
The cylndrical surface CS of main wheel hub 51 axially extends between main helical blade 17.Main helical margin 47 engages hermetically with the lock helicoid 23 of lock helical blade 27 along main helical blade 17 when they relative to each other rotate.Lock helical margin 48 engages hermetically with the main helicoid 21 of main helical blade 17 along lock helical blade 27 when they relative to each other rotate.Main wheel hub 51 and brake wheel hub 53 are straight in the axial direction, and are defined as around main axis 16 and lock axis 18.Main wheel hub and brake wheel hub can be hollow or solid.
When axially observing, main helical blade 17 and lock helical blade 27 are recognized as main lobe type part 57 and lock blade profile part 67 as shown in Figure 7.Exemplary compressor 8 shown in Fig. 1 to Fig. 7 has three main lobe type parts 57 and four lock blade profile parts 67.Less body clearance CL remains between compressor housing 9 (shown in the dotted line in Fig. 7) and main rotor 12 and gate rotor 7.Between main rotor 12 and gate rotor 7, self pass through the timing gear 84 of gear-box 82 as disclosed and keep less axial clearance AC (shown in Fig. 4).For the assembly 15 of two rotors, the number of lock blade profile part is than the number one more or less of main lobe type part.Main radius R M and lock radius R the G respectively overall diameter from main axis 16 and lock axis 18 to the main helical blade 17 of main rotor 12 and the lock helical blade 27 of gate rotor 7 record to height H.Main radius R M and lock radius R G can have about equally or length not etc.Main radius R M is shown longer than lock radius R G in Fig. 7.
Shown in Fig. 8 is the compressor 8 of exemplary shaft streaming entrance positive displacement gas turbine engine, and it has a main rotor and two or more gate rotor, and it represents the member 3 of axial flow entrance positive displacement gas turbine engine.Compressor 8 shown in Fig. 8 and Fig. 9 has main rotor 12 and the first gate rotor 13 and the second gate rotor 14.Referring to Fig. 9, compressor 8 has the first compressing section 24 and the second compressing section 26 between entrance changeover portion 28 and outlet changeover portion 30.Entrance changeover portion 28, the first compressing section 24 and the second compressing section 26, and 30 one-tenths of changeover portions of outlet crossfire relation downstream, and be designed to flow to continuously vertically and pass in order to compression the working fluid 25 of compressor 8.First paragraph 24 and second segment 26 have respectively different the first torsion slopes 34 and second and reverse slope 36.As described above, reverse slope corresponding to the pitch of the helical blade of rotor.
Referring to Fig. 8 and Fig. 9, at the compressor 8 shown in this, comprise rotor assembly 15, this rotor assembly 15 has main rotor 12 and the first gate rotor 13 and the second gate rotor 14 that extends to outlet 22 from axial flow entrance 20.Main rotor 12 has respectively and the first lock helical blade 27 of the first gate rotor 13 and the intermeshing main helical blade 17 of the second lock helical blade 29 of the second gate rotor 14.Main helical blade 17 radially outwards extends from the annular main wheel hub 51 of main rotor 12, and this annular main wheel hub 51 is defined as around main axis 16.The first lock helical blade 27 and the second lock helical blade 29 radially outwards extend from the first annular brake wheel hub 53 and the second brake wheel hub 55 of the first gate rotor 13 and the second gate rotor 14, and this first brake wheel hub 53 and the second brake wheel hub 55 are defined as respectively around the first lock axis 19 and the second lock axis 39.
Referring to Fig. 8 to Figure 12, rotor assembly 15 includes mouthful changeover portion 28 and outlet changeover portion 30, to hold the axial flow through compressor 8.As Figure 10 and Figure 11 more specifically illustrate, main helical blade 17 has leading edge 117, and it is transitioned into the blade profile launching completely in entrance changeover portion 28, from 0 radial height, becomes as from main wheel hub 51 with along the measured overall diameter of downstream direction D to height H.Term " completely launch blade profile " is defined as from the measured overall diameter of main wheel hub 51 to height H.As more specifically illustrated in Figure 12, main helical blade 17 has trailing edge 217, and it is the blade profile transition from launching completely in outlet changeover portion 30, becomes as from 0 measured radial height of main wheel hub 51 from overall diameter to height H.An alternative of compressor 8 does not comprise outlet changeover portion 30.
As shown in Figure 10, main helical blade 17 parts of passing entrance changeover portion 28 are leading edge 117, and can be described as helical, and scan backward or downstream.Scanning leading edge 117 is separated to the mass flow entering in the rotor channel launching completely reposefully.For using the member designs of taking turns speed at the high rotor during rotor relative reference is with over-one Mach number, this section can occupy the not very little part of whole compressor or member length.
Fig. 8 and Fig. 9 show the compressor 8 of the axial flow entrance positive displacement gas turbine engine with rotor assembly 15, this rotor assembly 15 has three rotors that extend to axial flow outlet 22 from axial flow entrance 20, comprises main rotor 12 and the first gate rotor 13 and the second gate rotor 14.Axial flow entrance 20 comprises crossing main loop opening 10 and the lock annular opening 11 radially extending between compressor housing 9 and main wheel hub 51 and brake wheel hub 53 respectively.Stream 40 is disposed radially between main wheel hub 51 and brake wheel hub 53 and housing 9, and axially extends to downstream axial flow outlet 22 from axial flow entrance 20.
Stream 40 comprises the main rotor stream 45 that roughly holds main rotor 12, and main helical blade 17 can be via 45 rotations of main rotor stream.Annular central flowpath segment 70 for main rotor 12 is radially arranged between the ring-shaped cylinder foreign steamer hub face 72 of main wheel hub 51 and the annular inner casing dignity 74 of housing 9, and radially extends between entrance changeover portion 28 and outlet changeover portion 30.Main rotor stream 45 comprises entrance flowpath segment 76, annular central flowpath segment 70 and outlet flowpath segment 78 with crossfire relation downstream.
In the inlet streams section 76 for main rotor shown in Fig. 8 and Figure 11, via entrance changeover portion 28, between the annular entry wheel hub surface 90 of main wheel hub 51 and brake wheel hub 53 and the annular entry housing face 92 of housing 9, extend.Annular entry wheel hub surface 90 and annular entry housing face 92 are shown taper shape, but also can be such as columniform other shape.Inlet streams section 76 has circular crosssection area CA, and it increases along downstream direction D or direction from front to back.Therefore, the annular entry area A I in inlet streams section 76 is less than the annular exit area A O in inlet streams section 76.Outlet flowpath segment 78 is extended between the annular exit wheel hub surface 94 of main wheel hub 51 and brake wheel hub 53 and the annular exit housing face 96 of housing 9 via outlet changeover portion 30.Annular exit wheel hub surface 94 and annular exit housing face 96 are shown taper shape, but also can be such as columniform other shape.Outlet flowpath segment 78 has circular crosssection area CA, and it reduces along downstream direction D or direction from front to back.Therefore, the annular entry area of outlet flowpath segment 78 is greater than the annular exit area A O of outlet flowpath segment 78.Inlet streams section 76 and outlet flowpath segment 78 contribute to provide the full axial flow that runs through compressor 8, comprise through axial flow entrance 20 and axial flow outlet 22.
Referring to Fig. 8 and Figure 11, the first compressing section 24 of rotor assembly 15 and compressor 8 and the second compressing section 26 are positioned between entrance changeover portion 28 and outlet changeover portion 30 with crossfire relation downstream.Rotor assembly 15 provides the Continuous Flow via entrance 20 and outlet 22 at compressor 8 duration of works.Independent filling air 50 is captured and is trapped in wherein by first paragraph 24.The compression of inflation 50 is along with inflation is passed to second segment 26 and occurs from first paragraph 24.Therefore, all fill air 50 is all compressed respectively at it when first paragraph 24 and second segment 26 are in the two.
Main rotor and gate rotor all can be around its corresponding axis rotations, and main rotor 12 can be different from the first gate rotor 13 and the second gate rotor 14 circumferencial direction but to rotate by the determined same rotational speed of fixed relationship.As shown in Figure 16, main rotor 12 is shown and can turns clockwise, and the first gate rotor 13 and the second gate rotor 14 are shown and can rotate by counter-clockwise CC.Therefore, main rotor 12, the first gate rotor 13 and the second gate rotor 14 link together with gear, and fixing speed ratio and phase relationship that they are always provided with the gearing 80 schematically showing in Figure 17 are relative to each other rotated.Power in order to drive compression machine 8 can be supplied with via line shaft 37, and line shaft 37 is shown and is connected on main rotor 12, as shown in Figure 17.The first gate rotor 13 and the second gate rotor 14 link together with gear by the timing gear 84 of gearing 80, to provide rotor rotation suitably regularly, and there is minimum and controlled gap between their the main helical blade 17 of spiral form and the first lock helical blade 27 and the second lock helical blade 29 of engagement.
Referring to Fig. 9 and Figure 11, main helical blade 17 has main helicoid 21, and the first lock helical blade 27 and the second lock helical blade 29 have respectively the first lock helicoid 23 and the second lock helicoid 33.Main helical blade 17 radially outwards extends from the cylndrical surface CS of the annular main wheel hub 51 of main rotor 12.The first lock helical blade 27 and the second lock helical blade 29 radially outwards extend from the first brake wheel hub 53 and the second brake wheel hub 55.
The cylndrical surface CS of main wheel hub 51 axially extends between main helical blade 17.Main helical margin 47 engages hermetically respectively with the first lock helicoid 23 of the first lock helical blade 27 and the second lock helicoid 33 of the second lock helical blade 29 along main helical blade 17 when they relative to each other rotate.The first lock helical margin 48 and the second lock helical margin 49 engage hermetically with the main helicoid 21 of main helical blade 17 along the first lock helical blade 27 and the second lock helical blade 29 when they relative to each other rotate.The first brake wheel hub 53 and the second brake wheel hub 55 are defined as respectively around the first lock axis 19 and the second lock axis 39, and are defined as around the brake wheel hub of lock axis in the axial direction for straight.Main wheel hub and brake wheel hub can be hollow.
Main rotor 12, the first gate rotor 13 and the second gate rotor 14 for the blade structure of rotor shown in Fig. 8 and Fig. 9 have been shown in the axial cross section in Figure 13.As shown in Figure 13, main rotor 12, the first gate rotor 13 and the second gate rotor 14 have lock blade profile part 67, the first rotor blade profile part 68 and the second rotor blade profile part 69 that corresponds respectively to main helical blade 17 and the first lock helical blade 27 and the second lock helical blade 29.Housing 9 is shown in broken lines.If main rotor 12 has M main lobe type part 57 or main helical blade 17, and first gate rotor 13 and the second gate rotor 14 there is N the first rotor blade profile part 68 or the first lock helical blade 27 and N the second rotor blade profile part 69 or the second lock helical blade 29, N the first rotor blade profile part 68 and the second rotor blade profile part 69 are just N=M/2+1, and N and M are integer.This relation of N and M is for the structure of three rotors.Therefore, M=4 and N=3 are for the structure shown in Fig. 8, Fig. 9 and Figure 13.The constructive alternative of main rotor 12, the first gate rotor 13 and the second gate rotor 14 is shown and in Figure 14, has M=6 and N=4 with section form, and in Figure 15, is M=8 N=5.
Referring to Fig. 9, main helical blade 17 and the first lock helical blade 27 and the second lock helical blade 29 have respectively constant the first torsion slope 34 and second and reverse slope 36 in first paragraph 24 and second segment 26.Reverse slope and be defined as the cross section 41 of helix element (comprising the lock blade profile part 67 shown in Figure 13 to Figure 15, the first rotor blade profile part 68 and the second rotor blade profile part 69) at the rotating amount of the per unit distance along axis (main axis 16 as shown in Figure 9).Main rotor cross section 41 rotating 360 degrees have been shown in Fig. 9.
Reverse slope and be also 360 degree or 2Pi radian divided by for example, identical main helical margin 47 along helix element (, as shown in Figure 9 main helical blade 17 and lock helical blade 27) and the axial distance CD between two adjacent top 44 of lock helical margin 48.Axial distance CD is the distance of whole circle 43 helicals.For compressor, in first paragraph 24 first reverses slope 34 and is less than the torsion of second in second segment 26 slope 36, in second segment 26 second reverses slope 36 and in Fig. 2, is shown for single gate rotor structure, but is also applicable to have the structure of two or more gate rotors.
Figure 16 and Figure 17 schematically show respectively the embodiment 100 of two rotors and the embodiment 102 of three rotors of axial flow positive-displacement compressor 8.The embodiment 100 of two rotors as described above has rotor assembly 15, and this rotor assembly 15 has main rotor 12 and the gate rotor 7 that extends to axial flow outlet 22 from axial flow entrance 20.The axial flow of working fluid 25 is represented by arrow.The embodiment 102 of three rotors as described above has rotor assembly 15, and this rotor assembly 15 has three rotors that extend to axial flow outlet 22 from axial flow entrance 20, comprises main rotor 12 and the first gate rotor 13 and the second gate rotor 14.
In Figure 18 and Figure 19, schematically show the embodiment 100 of two rotors and the embodiment 102 of three rotors of axial flow positive displacement turbine or expander 88.The embodiment 100 of two rotors of expander 88 has rotor assembly 15, and this rotor assembly 15 has main rotor 12 and the gate rotor 7 that extends to axial flow outlet 22 from axial flow entrance 20.The embodiment 102 of three rotors of expander 88 has rotor assembly 15, and this rotor assembly 15 has main rotor 12 and the first gate rotor 13 and the second gate rotor 14 that extends to axial flow outlet 22 from axial flow entrance 20.
Different the first torsion slope 34 and second that the first expansion arc 124 of expander 88 and the second expansion arc 126 have respectively main helical blade 17 and lock helical blade 27 reverses slope 36.Main helical blade 17 and lock helical blade 27 have the first torsion slope 34 and the second torsion slope 36 in each person in the first expansion arc 124 and the second expansion arc 126 respectively.In expander 88, first in the first expansion arc 124 reverses slope 34 and is greater than the torsion of second in the second expansion arc 126 slope 36, and this is just in time contrary with compressor 8.
Power obtains from expander 88 via line shaft 37, and as shown in Figure 17 and Figure 18, line shaft 37 is shown to be connected on main rotor 12 and from main rotor 12 and extends backward or downstream, but also can extend forward or upstream from main rotor 12.Gate rotor is connected on main rotor by the timing gear 84 of gearing 80, to provide rotor rotation suitably regularly, and there is minimum and controlled gap between their main helical blade 17 and the first lock helical blade 27 and the second lock helical blade 29 of engagement.
As shown in Figure 21, for the embodiment 100 of two rotors shown in Figure 18, expander 88 has inlet streams section 76 and axial flow entrance 20, and axial flow entrance 20 comprises in the crossing main loop opening 10 and lock annular opening 11 being each defined between the main wheel hub 51 of expander housing 209 and main rotor 12 and the brake wheel hub 53 of gate rotor 7.Expander shown here also has the axial flow outlet 22 with the outlet flowpath segment 78 shown in Figure 21 and Figure 22.Axially extend between the corresponding main wheel hub 51 of main rotor 12 and gate rotor 7 and the annular entry wheel hub surface 90 of brake wheel hub 53 and the annular entry housing face 92 of housing 209 via entrance changeover portion 28 in inlet streams section 76 shown in Figure 20.Annular entry wheel hub surface 90 and annular entry housing face 92 are shown taper shape, but also can be such as columniform other shape.Inlet streams section 76 has circular crosssection area CA, and it increases along downstream direction D or direction from front to back.Therefore, the annular entry area A I in inlet streams section 76 is less than the annular exit area A O in inlet streams section 76.
In entrance changeover portion 28, main helical blade 17 is transitioned into completely the blade profile launching, on downstream direction D from 0 radial height become from main wheel hub 51 radially outwards and on axial downstream D measured overall diameter to height H.Lock helical blade 27 is transitioned into completely the blade profile launching, and on downstream direction D, from 0 radial height, becomes from brake wheel hub 53 measured full radial height outwards and on axial downstream D radially.
Outlet flowpath segment 78 shown in Figure 21 and Figure 22 is axially extended between the corresponding main wheel hub 51 of main rotor 12 and gate rotor 7 and the annular exit wheel hub surface 94 of brake wheel hub 53 and the annular exit housing face 96 of expander housing 209 via outlet changeover portion 30.Annular exit wheel hub surface 94 and annular exit housing face 96 are shown taper shape, but also can be such as columniform other shape.Outlet flowpath segment 78 has circular crosssection area CA, and it reduces along aspect, downstream D or direction from back to front.Therefore, the annular entry area A I of outlet flowpath segment 78 is greater than the annular exit area A O of outlet flowpath segment 78.Inlet streams section 76 and outlet flowpath segment 78 contribute to provide the full axial flow that runs through expander 88, comprise through axial flow entrance 20 and axial flow outlet 22, but maybe can have a small amount of or remaining eddy flow in the axial flow that flows out axial flow outlet 22.
In outlet changeover portion 30, the blade profile transition of main helical blade 17 from launching completely becomes from overall diameter to height H from main wheel hub 51 0 measured radial height outwards and on axial downstream D radially on downstream direction D.Lock helical blade 27 is the blade profile transition from launching completely also, becomes from main wheel hub 51 0 measured radial height outwards and on axial downstream D radially on downstream direction D from overall diameter to height H.
As shown in Figure 21, the trailing edge 217 that extends through the main helical blade 17 of outlet changeover portion 30 can be described as helical, and scans backward or downstream.Scanning trailing edge 217 contributes to prevent separated and prevents that eddy current from leaving helical blade end.Lock helical blade 27 also has the trailing edge of scanning 217, but they in shape from main helical blade 17 as shown in Figure 21 to scan trailing edge 217 different.
The trailing edge 217 of lock helical blade 27 is shown in the upstream direction crooked in Figure 21 and Figure 22, contrary with downstream direction D.These upstream crooked trailing edge 217 there is inner radial trailing edge 230 and radially outer trailing edge 232, this inner radial trailing edge 230 and radially outer trailing edge 232 scan backward along trailing edge 217 point of distance 235 in downstream being radially positioned between brake wheel hub 53 and expander housing 209.
In gaseous environment, High Mach number can limit high wheel speed work.For example, 0.5 air inlet Mach number and grade are that the wheel speed of the correction of 1000ft/sec (feet per second) will produce ultrasonic relevant blade inlet Mach number.Expectation be with even higher than the wheel speed work of 1000ft/sec, because now can shorten machinery or member.When the relevant Mach number of entrance approaches velocity of sound, the factor of shock at entry and obstruction utilizes plane rotor end to carry out the benefit of high speed operation seriously restriction.The leading edge of scanning through entrance outlet flowpath segment 76 helps avoid these problems.
Axial flow positive displacement engine component provides to be had high quality stream and has Efficient Compression and the engine design of the potentiality of expansion in each proparea.Positive displacement member designs also can provide volume mass velocity proportional to rotating speed, and the almost constant pressure ratio in wider velocity range.This combination provides for the thermodynamic process of compression, burning and expansion the chance of improving member and levels of system performance that is better than competitive turbine components.
As shown in Figure 23 to Figure 26, for turbine or expander 88, the member 3 of axial flow positive displacement gas turbine engine disclosed herein can have more than one main rotor.First structure in rotor assembly 15 with two main rotors 12 and a gate rotor 7 has been shown in Figure 23.Figure 24 illustrates second structure in rotor assembly 15 with two main rotors 12 and two gate rotors 7.In Figure 25, with axial cross section, show the vane collocation of first structure in rotor assembly 15 with two main rotors 12 and a gate rotor 7.All main axiss 16 and lock axis 18 that Figure 23 and Figure 25 also show main rotor 12 and gate rotor 7 are all coplanar.As alternative, as shown in Figure 26, the main axis 16 of main rotor 12 and gate rotor 7 and lock axis 18 can be not in one plane but be parallel.
Although described the content that is recognized as the preferred embodiments of the present invention and exemplary embodiment herein; but those skilled in the art will be clear that according to instruction content herein; the present invention can carry out other and revise, and therefore expectation is all protected all such modifications that fall in connotation of the present invention and scope in claims.Therefore, expectation is protected by patent certificate is as defined in claim and the present invention who is distinguished.

Claims (8)

1. a member for axial flow positive displacement gas turbine engine, comprising:
Rotor assembly, it extends to the axially isolated axial flow outlet in downstream from holoaxial streaming entrance,
Described rotor assembly comprises main rotor and one or more gate rotor,
Described main rotor and described gate rotor can be respectively around parallel main axis and the rotation of lock axis of described main rotor and described gate rotor,
Described main rotor and described gate rotor have respectively two or more main helical blades and two or more lock helical blades of reeling around described main axis and described lock axis,
Described main helical blade and described lock helical blade are intermeshing,
Described main helical blade and described lock helical blade radially outwards extend from being defined as around annular main wheel hub and the circular brake wheel hub of the main axis of described main rotor and the lock axis of described gate rotor;
Described axial flow entrance comprises respectively between the housing that surrounds described rotor assembly and main wheel hub and brake wheel hub radially crossing main loop opening and the lock annular opening of extension,
The middle body of described main helical blade extends vertically and downstream, and has from described main wheel hub measured full radial height outwards radially,
Entrance changeover portion in axial the place ahead and the upstream of described middle body, and
Described main helical blade is transitioned into from 0 radial height the blade profile launching completely in described entrance changeover portion, and the described blade profile launching completely has on downstream direction from the radially measured full radial height of described main wheel hub.
2. the member of axial flow positive displacement gas turbine engine according to claim 1, is characterized in that, described member also comprises:
At the axial rearward direction of described middle body and the outlet changeover portion in downstream, and
Described main helical blade is transitioned on downstream direction from 0 radially measured radial height of described main wheel hub from having the blade profile launching completely of described full radial height in described outlet changeover portion.
3. the member of axial flow positive displacement gas turbine engine according to claim 1, is characterized in that, described member also comprises the gearing that described main rotor and described gate rotor are linked together with gear.
4. the member of axial flow positive displacement gas turbine engine according to claim 1, is characterized in that, described member also comprises:
Stream, it is disposed radially between described main wheel hub and described brake wheel hub and described housing, and extends to downstream vertically described axial flow outlet from described axial flow entrance;
Described main helical blade and described lock helical blade can rotate in described stream;
Described stream comprises with crossfire relation downstream inlet streams section, the annular central flowpath segment being arranged in described entrance changeover portion, and is arranged on the outlet flowpath segment in outlet changeover portion, and
The annular entry area in described inlet streams section is less than the annular exit area in described inlet streams section.
5. the member of axial flow positive displacement gas turbine engine according to claim 4, is characterized in that, described member also comprises the outlet flowpath segment with the circular crosssection area reducing along described downstream direction.
6. a compressor for axial flow positive displacement gas turbine engine, comprising:
Rotor assembly, it extends to the axially isolated axial flow outlet in downstream from holoaxial streaming entrance,
Described rotor assembly comprises main rotor and one or more gate rotor,
Described main rotor and described gate rotor can be respectively around parallel main axis and the rotation of lock axis of described main rotor and described gate rotor,
Described main rotor and described gate rotor have respectively two or more main helical blades and two or more lock helical blades of reeling around described main axis and described lock axis,
Described main helical blade and described lock helical blade are intermeshing,
Described main helical blade and described lock helical blade radially outwards extend from being defined as around annular main wheel hub and the circular brake wheel hub of the main axis of described main rotor and the lock axis of described gate rotor,
The main helical blade of described rotor assembly has respectively the first different main torsion slopes and the second main torsion slope in first paragraph and second segment, and the lock helical blade of described rotor assembly has respectively in described first paragraph and described second segment, and the first different locks reverses slope and the second lock reverses slope
Described the first main torsion slope and described the first lock reverse slope and are less than respectively described the second main torsion slope and described the second lock torsion slope,
Described axial flow entrance comprises respectively between the housing that surrounds described rotor assembly and main wheel hub and brake wheel hub radially crossing main loop opening and the lock annular opening of extension,
The middle body of described main helical blade extends vertically and downstream, and has from described main wheel hub measured full radial height outwards radially,
Entrance changeover portion in axial the place ahead and the upstream of described middle body, and
Described main helical blade is transitioned into from 0 radial height the blade profile launching completely in described entrance changeover portion, and the described blade profile launching completely has on downstream direction from the radially measured full radial height of described main wheel hub.
7. an expander for axial flow positive displacement gas turbine engine, comprising:
Rotor assembly, it extends to the axially isolated axial flow outlet in downstream from holoaxial streaming entrance,
Described rotor assembly comprises main rotor and one or more gate rotor,
Described main rotor and described gate rotor can be respectively around parallel main axis and the rotation of lock axis of described main rotor and described gate rotor,
Described main rotor and described gate rotor have respectively two or more main helical blades and two or more lock helical blades of reeling around described main axis and described lock axis,
Described main helical blade and described lock helical blade are intermeshing,
Described main helical blade and described lock helical blade radially outwards extend from being defined as around annular main wheel hub and the circular brake wheel hub of the main axis of described main rotor and the lock axis of described gate rotor,
The main helical blade of described rotor assembly has respectively the first different main torsion slopes and the second main torsion slope in first paragraph and second segment, and the lock helical blade of described rotor assembly has respectively in described first paragraph and described second segment, and the first different locks reverses slope and the second lock reverses slope
Described the first main torsion slope and described the first lock reverse slope and are greater than respectively described the second main torsion slope and described the second lock torsion slope,
Described axial flow entrance comprises respectively between the housing that surrounds described rotor assembly and main wheel hub and brake wheel hub radially crossing main loop opening and the lock annular opening of extension,
The middle body of described main helical blade extends vertically and downstream, and has from described main wheel hub measured full radial height outwards radially,
Entrance changeover portion in axial the place ahead and the upstream of described middle body, and
Described main helical blade is transitioned into from 0 radial height the blade profile launching completely in described entrance changeover portion, and the described blade profile launching completely has on downstream direction from the radially measured full radial height of described main wheel hub.
8. a member for axial flow positive displacement gas turbine engine, comprising:
Rotor assembly, it extends to the axially isolated axial flow outlet in downstream from holoaxial streaming entrance,
Described rotor assembly comprises one or more main rotors and one or more gate rotor,
Described main rotor and described gate rotor can be respectively around parallel main axis and the rotation of lock axis of described main rotor and described gate rotor,
Described main rotor and described gate rotor have respectively two or more main helical blades and two or more lock helical blades of reeling around described main axis and described lock axis,
Described main helical blade and described lock helical blade are intermeshing,
Described main helical blade and described lock helical blade radially outwards extend from being defined as around annular main wheel hub and the circular brake wheel hub of the main axis of described main rotor and the lock axis of described gate rotor;
Described axial flow entrance comprises respectively between the housing that surrounds described rotor assembly and main wheel hub and brake wheel hub radially crossing main loop opening and the lock annular opening of extension,
The middle body of described main helical blade extends vertically and downstream, and has from described main wheel hub measured full radial height outwards radially,
Entrance changeover portion in axial the place ahead and the upstream of described middle body, and
Described main helical blade is transitioned into from 0 radial height the blade profile launching completely in described entrance changeover portion, and the described blade profile launching completely has on downstream direction from the radially measured full radial height of described main wheel hub.
CN200910113700.0A 2008-12-31 2009-12-31 Positive displacement gas turbine engine with parallel screw rotors Expired - Fee Related CN101769165B (en)

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CA2689175C (en) 2017-05-09
RU2009148668A (en) 2011-07-10
JP2010164047A (en) 2010-07-29
JP5647411B2 (en) 2014-12-24
US20100166591A1 (en) 2010-07-01
RU2532637C2 (en) 2014-11-10
CN101769165A (en) 2010-07-07
US8328542B2 (en) 2012-12-11
CA2689175A1 (en) 2010-06-30
EP2204532A2 (en) 2010-07-07
EP2204532A3 (en) 2014-10-08

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